Innosat
The MATS mission is based on the development of the InnoSat spacecraft concept. The InnoSat spacecraft is a small, capable and low-cost platform intended for a range of scientific research missions in Low Earth Orbit.
The InnoSat spacecraft is designed to fit within a piggyback launch envelope, that is roughly 50 kg mass and 70×60×85 cm size, and to provide high performances in terms of pointing, power and data downlink.
The InnoSat Platform has been designed to maximize the use of the launcher volume available for a piggyback launch. The main drivers behind this are simply the power and volume needed for the payload.
A key factor of being able to meet those demands is to baseline a dawn/dusk orbit or go to a sun pointing mode. Having the sun from one side reduces the amount of necessary solar panels in different directions, which allows for greater flexibility for the payload accommodation.
All platform avionics are accommodated into one module, called the Service Module. This module has a launch vehicle adapter on one side and a payload interface on the other side.
The standard InnoSat platform
- S/C mass and size: 70 x 60 x 85 cm, ~50 kg (incl. payload)
- Max payload size: 65 x 53 x 48 cm (blue volume)
- Max payload mass: 15 kg
- Max payload power: 40 W (average)
- Solar array: 170 W installed power
- Downlink bitrate: 3-5 Mbps (S-band)
- Stabilization: 3-axis with RW and Star Tracker
- Orbit: 550 to 650 km dawn/dusk (SSO)
- Orbit determination: On-board GPS
- Payload can be Earth- Limb- or Space-facing
Last updated: November 4, 2022
Source: MISU